公开(公告)号：WO2006112807A2

公开(公告)日：2006-10-26

申请号：PCT/US2004039998

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP ,  ROBERGE GARY D

Inventor： ROBERGE GARY D

IPC: F02C7/26 ,  F02C3/073 ,  F02C7/27 ,  F02K3/068

CPC classification number: F02C7/26 ,  F02C3/073 ,  F02C7/27 ,  F02K3/068 ,  F05D2240/12

Abstract: In order to start a turbine engine, high-pressure fluid is directed onto a turbine to cause rotation of the turbine and thereby start the turbine engine. In a disclosed embodiment, the high-pressure fluid is provided through a fluid outlet in a vane positioned adjacent the turbine. The high-pressure fluid is provided by an air source, which may be another turbine engine, especially where the turbine engine to be started is a tip turbine engine that is not the primary propulsion source.

Abstract translation: 为了启动涡轮发动机，将高压流体引导到涡轮机上以引起涡轮机的旋转，从而启动涡轮发动机。 在公开的实施例中，高压流体通过位于涡轮附近的叶片中的流体出口提供。 高压流体由空气源提供，空气源可以是另一个涡轮发动机，特别是在要启动的涡轮发动机是不是主要推进源的末端涡轮发动机的情况下。

公开(公告)号：WO2006110123A2

公开(公告)日：2006-10-19

申请号：PCT/US2004039997

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP ,  ROBERGE GARY D

Inventor： ROBERGE GARY D

IPC: F02K1/00 ,  F02K3/068

CPC classification number: F02K1/006 ,  F02K3/068

Abstract: A transition duct is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of the transition duct. The transition duct incorporates a perimeter slot providing cooling to the duct outer wall and attached components. The variable vanes are installed to vector the exhaust gases. This allows the aircraft to decelerate, hover or accelerate in the forward direction by commanding the position of the variable vanes. One potential application of the tip turbine engine is for vertical installations in aircraft.

Abstract translation: 在涡轮发动机的出口处设置有过渡管道。 过渡管道将尖端涡轮发动机的出口从圆形过渡到矩形。 过渡管道还在过渡管道的出口处提供多个可变叶片。 过渡管道包含一个周边槽口，为管道外壁和连接部件提供冷却。 安装可变叶片以对废气进行传播。 这允许飞机通过指示可变叶片的位置来向前方向减速，悬停或加速。 尖端涡轮发动机的一个潜在应用是飞机中的垂直安装。

公开(公告)号：DE602007004531D1

公开(公告)日：2010-03-18

申请号：DE602007004531

申请日：2007-06-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D

IPC: B64C27/18 ,  B64C27/24

公开(公告)号：BRPI0800345A

公开(公告)日：2008-11-04

申请号：BRPI0800345

申请日：2008-03-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D ,  LEJAMBRE CHARLES R ,  WATSON CHARLES R

IPC: F02C7/042

Abstract: A variable area fan nozzle (40) for use with a gas turbine engine system (10) includes a nozzle section (56, 56') that is movable between a plurality of positions to change an effective area (AR, AR 2 , AR') associated with a bypass airflow (D) through a fan bypass passage (30) of a gas turbine engine (10). A protective coating (74) is disposed on the nozzle section (56, 56') and resists change in the effective area (AR, AR 2 , AR') of the nozzle section caused by environmental conditions.

公开(公告)号：CA2618116A1

公开(公告)日：2008-09-22

申请号：CA2618116

申请日：2008-01-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D ,  LEJAMBRE CHARLES R ,  WATSON CHARLES R

IPC: F01D9/02 ,  B05D5/08 ,  C09K3/18 ,  F01D25/02 ,  F02C9/18

Abstract: A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass airflow through a fan bypass passage of a gas turbine engine. A protective coating is disposed on the nozzle section and resists change in the effective area of the nozzle section caused by environmental conditions.

公开(公告)号：EP3071793A4

公开(公告)日：2017-12-06

申请号：EP14879065

申请日：2014-10-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D

IPC: F01D5/14 ,  B23P15/04 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F01D25/00 ,  F01D25/12 ,  F04D29/32

CPC classification number: F01D5/282 ,  B23P15/04 ,  F01D5/147 ,  F01D5/18 ,  F01D5/284 ,  F01D9/041 ,  F01D25/005 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2260/36 ,  F05D2300/5023 ,  F05D2300/522 ,  Y02T50/672

Abstract: A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.

公开(公告)号：EP3080424A4

公开(公告)日：2017-08-02

申请号：EP14869066

申请日：2014-09-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D

IPC: F02C3/073 ,  F01D5/14 ,  F01D5/22 ,  F02C7/04 ,  F02K3/06 ,  F02K3/068 ,  F02K3/072

CPC classification number: F02C3/04 ,  F01D13/006 ,  F02C3/073 ,  F02K3/06 ,  F02K3/068 ,  F02K3/072 ,  F05D2220/32 ,  F05D2220/323 ,  Y02T50/672

Abstract: A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an inlet of a reverse-core gas generator, and a second portion, configured to receive air from an exit of the gas generator and direct the air forward and radially outward of the propulsor, toward the fan-tip turbine in the propulsor, thereby driving the propulsor.

Abstract translation: 一种反向堆芯涡轮风扇发动机，其包括推进器部分，所述推进器部分包括风扇和风扇叶顶涡轮，所述推进器部分构造成将空气输送到芯管，所述芯管包括设置在推进器部分的后部的第一部分以及将空气引导向尾部朝向 以及第二部分，所述第二部分构造成从所述气体发生器的出口接收空气，并将所述空气朝向所述推进器的所述风扇尖端涡轮机推进，从而驱动所述推进器。

公开(公告)号：EP2964943A4

公开(公告)日：2016-04-06

申请号：EP14759448

申请日：2014-02-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D

IPC: F02K1/82 ,  F01D25/08 ,  F01D25/24 ,  F01D25/26 ,  F01D25/28 ,  F01D25/30 ,  F02C7/20

CPC classification number: F02K1/822 ,  F01D25/08 ,  F01D25/243 ,  F01D25/26 ,  F01D25/28 ,  F01D25/30 ,  F02C7/18 ,  F02C7/20 ,  F05D2230/642 ,  F05D2250/241 ,  F05D2260/30 ,  F23R3/005 ,  Y02T50/675

Abstract: The exhaust system (60) includes an exhaust flow path liner (62) surrounded and supported by a plurality of structural duct segments (64, 70). Pluralities of links (84) are secured to and extend between the duct segments (64, 70) and the liner (62). A duct end (88) of the link includes a lock member (96) having a diameter greater than a width of the stem (86). The lock member (96) is configured to be secured within a capture nest (98) defined between and within adjacent junction flanges (76, 80} of the structural duct segments {64, 70) when the segments (64, 70) are secured to each other to secure the segments (64, 70) together. A catch member (100) at an opposed end of the link (84) is secured to a capture node (102) at the exhaust liner (62).

公开(公告)号：EP2971697A4

公开(公告)日：2016-11-16

申请号：EP13878238

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D

IPC: F02C7/32 ,  F01D25/24

CPC classification number: F02C7/32 ,  B64D29/08 ,  F01D25/28 ,  F02C7/36 ,  F05D2220/50 ,  F05D2230/60 ,  F05D2240/40 ,  Y10T29/49321

Abstract: An accessory drive system for an aircraft gas turbine engine is disclosed. The system may comprise an engine case including a core engine cowl and at least a first accessory drive gearbox disposed within the core engine cowl. The at least first accessory drive gearbox may be operatively connected to one or more accessories remotely located therefrom.

公开(公告)号：EP2971551A4

公开(公告)日：2016-11-02

申请号：EP13878165

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D

IPC: F01D5/22 ,  F01D5/02 ,  F01D5/12 ,  F01D5/14 ,  F01D5/28 ,  F01D5/30 ,  F01D5/34 ,  F02C7/00 ,  F02K3/06

CPC classification number: F01D5/02 ,  F01D5/147 ,  F01D5/225 ,  F01D5/282 ,  F01D5/3069 ,  F01D5/34 ,  F02C3/04 ,  F02K3/06 ,  F04D29/023 ,  F04D29/321 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49323

Abstract: In accordance with one aspect of the disclosure, a fan section for a gas turbine engine is disclosed. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.

Abstract translation: 根据本公开的一个方面，公开了一种用于燃气涡轮发动机的风扇部分。 风扇可以包括转子盘和固定地附接到转子盘并且由转子盘支撑的多个翼型件作为单个整体件。 翼型件可相对于发动机轴线从转子盘径向向外延伸。 转子盘可以由金属制成，翼型件可以至少部分地由有机基质复合材料制成。